EP2971671B1 - Bauteil, zugehöriges gasturbinentriebwerk und verfahren zum kühlen eines bauteils - Google Patents

Bauteil, zugehöriges gasturbinentriebwerk und verfahren zum kühlen eines bauteils Download PDF

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Publication number
EP2971671B1
EP2971671B1 EP14767715.7A EP14767715A EP2971671B1 EP 2971671 B1 EP2971671 B1 EP 2971671B1 EP 14767715 A EP14767715 A EP 14767715A EP 2971671 B1 EP2971671 B1 EP 2971671B1
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EP
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Prior art keywords
channel
component
recited
gas turbine
turbine engine
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EP14767715.7A
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English (en)
French (fr)
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EP2971671A1 (de
EP2971671A4 (de
Inventor
Scott H. LAMSON
Andrew D. Milliken
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RTX Corp
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United Technologies Corp
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/24—Heat or noise insulation
    • F02C7/25—Fire protection or prevention
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/127—Vortex generators, turbulators, or the like, for mixing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/15—Two-dimensional spiral
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/204—Heat transfer, e.g. cooling by the use of microcircuits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes

Definitions

  • This disclosure relates to a gas turbine engine, and more particularly to a gas turbine engine component having cooling channels arranged to counteract vortices associated with film injection.
  • Gas turbine engines typically include a compressor section, a combustor section and a turbine section. During operation, air is pressurized in the compressor section and is mixed with fuel and burned in the combustor section to generate hot combustion gases. The hot combustion gases are communicated through the turbine section, which extracts energy from the hot combustion gases to power the compressor section and other gas turbine engine loads.
  • cooling schemes that circulate airflow to cool the component during engine operation. Thermal energy is transferred from the component to the airflow as the airflow circulates through the cooling scheme to cool the component.
  • EP 2131109 , EP 2131108 , US 3525486 and US 4529358 all relate to gas turbine engine components.
  • FIG. 1 schematically illustrates a gas turbine engine 20.
  • the exemplary gas turbine engine 20 is a two-spool turbofan engine that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include an augmenter section (not shown) among other systems for features.
  • the fan section 22 drives air along a bypass flow path B, while the compressor section 24 drives air along a core flow path C for compression and communication into the combustor section 26.
  • the hot combustion gases generated in the combustor section 26 are expanded through the turbine section 28.
  • FIG. 1 schematically illustrates a gas turbine engine 20.
  • the exemplary gas turbine engine 20 is a two-spool turbofan engine that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28.
  • Alternative engines might include an augmenter section (not shown) among other systems for features.
  • the fan section 22 drives air along a bypass flow path B, while the compressor section 24 drives
  • the gas turbine engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine centerline longitudinal axis A.
  • the low speed spool 30 and the high speed spool 32 may be mounted relative to an engine static structure 33 via several bearing systems 31. It should be understood that other bearing systems 31 may alternatively or additionally be provided.
  • the low speed spool 30 generally includes an inner shaft 34 that interconnects a fan 36, a low pressure compressor 38 and a low pressure turbine 39.
  • the inner shaft 34 can be connected to the fan 36 through a geared architecture 45 to drive the fan 36 at a lower speed than the low speed spool 30.
  • the high speed spool 32 includes an outer shaft 35 that interconnects a high pressure compressor 37 and a high pressure turbine 40.
  • the inner shaft 34 and the outer shaft 35 are supported at various axial locations by bearing systems 31 positioned within the engine static structure 33.
  • a combustor 42 is arranged between the high pressure compressor 37 and the high pressure turbine 40.
  • a mid-turbine frame 44 may be arranged generally between the high pressure turbine 40 and the low pressure turbine 39.
  • the mid-turbine frame 44 can support one or more bearing systems 31 of the turbine section 28.
  • the mid-turbine frame 44 may include one or more airfoils 46 that extend within the core flow path C.
  • the inner shaft 34 and the outer shaft 35 are concentric and rotate via the bearing systems 31 about the engine centerline longitudinal axis A, which is colinear with their longitudinal axes.
  • the core airflow is compressed by the low pressure compressor 38 and the high pressure compressor 37, is mixed with fuel and burned in the combustor 42, and is then expanded over the high pressure turbine 40 and the low pressure turbine 39.
  • the high pressure turbine 40 and the low pressure turbine 39 rotationally drive the respective high speed spool 32 and the low speed spool 30 in response to the expansion.
  • the pressure ratio of the low pressure turbine 39 can be pressure measured prior to the inlet of the low pressure turbine 39 as related to the pressure at the outlet of the low pressure turbine 39 and prior to an exhaust nozzle of the gas turbine engine 20.
  • the bypass ratio of the gas turbine engine 20 is greater than about ten (10:1)
  • the fan diameter is significantly larger than that of the low pressure compressor 38
  • the low pressure turbine 39 has a pressure ratio that is greater than about five (5:1). It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present disclosure is applicable to other gas turbine engines, including direct drive turbofans.
  • TSFC Thrust Specific Fuel Consumption
  • Fan Pressure Ratio is the pressure ratio across a blade of the fan section 22 without the use of a Fan Exit Guide Vane system.
  • the low Fan Pressure Ratio according to one non-limiting embodiment of the example gas turbine engine 20 is less than 1.45.
  • Low Corrected Fan Tip Speed is the actual fan tip speed divided by an industry standard temperature correction of [(Tram°K)/(288.17°K)] 0.5 ([(Tram°R)/(518.7°R)] 0.5 ).
  • the Low Corrected Fan Tip Speed according to one non-limiting embodiment of the example gas turbine engine 20 is less than about 351 m/s (1150 fps).
  • Each of the compressor section 24 and the turbine section 28 may include alternating rows of rotor assemblies and vane assemblies (shown schematically) that carry airfoils that extend into the core flow path C.
  • the rotor assemblies can carry a plurality of rotating blades 25, while each vane assembly can carry a plurality of vanes 27 that extend into the core flow path C.
  • the blades 25 create or extract energy (in the form of pressure) from the core airflow that is communicated through the gas turbine engine 20 along the core flow path C.
  • the vanes 27 direct the core airflow to the blades 25 to either add or extract energy.
  • Various components of a gas turbine engine 20 may be subjected to repetitive thermal cycling under widely ranging temperatures and pressures.
  • the hardware of the turbine section 28 is particularly subjected to relatively extreme operating conditions. Therefore, some components may require dedicated cooling systems to cool the parts during engine operation.
  • This disclosure relates to cooling channel pairs that may be incorporated into the components of the gas turbine engine as part of a cooling system for counteracting naturally induced vortex pairs associated with film injection.
  • Figure 2 illustrates a component 60 having an internal cooling system 65 for circulating a cooling fluid, such as relatively cool air from the compressor section 24, to cool the component 60.
  • the component 60 is a turbine blade of the turbine section 28. It is to be understood; however, that the embodiments described herein are not limited to blades or airfoils and can also be applied to blade outer air seals (BOAS), combustor liners, case structures, turbine exhaust case liners or other components that utilize dedicated internal cooling, for example.
  • BOAS blade outer air seals
  • the component 60 has a body 62 that defines an external and internal shape with respect to internal passages.
  • the body 62 extends between a leading edge LE and a trailing edge TE and may include an airfoil section 64, a platform 66 and a root 68.
  • the airfoil section 64 extends outwardly from the platform 66 and the root 68 extends outwardly in an opposed direction from the platform 66.
  • the exemplary cooling system 65 includes two or more internal micro-channels formed inside the body 62, portions of which are schematically shown as 70A, 70B (hereafter "first channel 70A” and “second channel 70B").
  • first and second channels 70A, 70B may be fed with cooling fluid from a main cooling cavity of the component 60.
  • the first and second channels 70A, 70B can be micro-channels that have a maximum diameter of less than 0.635 millimeters (0.025 inches).
  • the first and second channels 70A, 70B define a maximum diameter of less than 0.5 millimeters (0.020 inches).
  • a maximum diameter of the first and second channels 70A, 70B is less than 0.25 millimeters (0.010 inches).
  • the relatively small dimensioned first and second channels 70A, 70B may also be referred to as vascular channels.
  • Figure 3 illustrates a magnified, isolated view of the first channel 70A and the second channel 70B of the cooling system 65.
  • the first and second channels 70A, 70B can extend through a wall 72 of the body 62, such as an internal or external wall.
  • the first and second channels 70A, 70B are depicted in Figure 2 as being located inside the airfoil section 64, the first and second channels 70A, 70B can alternatively be located in the platform 66 or root 68, or can span between two or more of the airfoil section 64, platform 66 and root 68.
  • each of the first and second channels 70A, 70B extend along an axis 74 and include a plurality of twists 76.
  • the first and second channels 70A, 70B may be linear or non-linear.
  • the first and second channels 70A, 70B may twist, by a twist amount in degrees, with respect to the axes 74 to establish the plurality of twists 76.
  • the first and second channels 70A, 70B twist one or more rotations (greater than or equal to 365°) about the axes 74.
  • first and second channels 70A, 70B are helical shaped.
  • a cross-section taken perpendicular to the axes 74 is, according to the invention, elliptical.
  • said cross-section may be semi-circular for example.
  • each channel 70A, 70B serve to produce a desired type of swirling flow of a cooling fluid through the first and second channels 70A, 70B.
  • the swirling flow may define a swirl vector that is parallel to the axes 74, which may enhance the cooling effect in the component 60.
  • the swirl vector increases a co-efficient of heat transfer between the cooling fluid and the body 62 of the component 60.
  • the twist amount and diameter of each of the first and second channels 70A, 70B provide enhanced cooling capability in the component 60.
  • the first channel 70A and the second channel 70B may be positioned adjacent to one another such that a distance D extends between the axes 74.
  • the dimension of the distance D may vary depending on design specific parameters including the amount of required cooling, among other factors.
  • the first channel 70A and the second channel 70B may be parallel to one another.
  • the first channel 70A may extend to a first outlet 80 and the second channel 70B may extend to a second outlet 82.
  • the outlets 80, 82 may extend through the wall 72.
  • the outlets 80, 82 may include any shape for discharging cooling fluid from the first and second channels 70A, 70B, such as via film injection.
  • the first and second channels 70A, 70B are configured to communicate cooling fluid along opposite flow paths.
  • the first channel 70A may define a first swirl flow path S1 of a cooling fluid 69 and the second channel 70B may define a second swirl flow path S2 of cooling fluid 69 that is opposite of the first swirl flow path S1.
  • the flow of the cooling fluid 69 swirls in opposite directions inside the first channel 70A and the second channel 70B, as further discussed below.
  • the second channel 70B may be oriented to define the opposite swirl flow path S2 by displacing its twists 76 by 180° relative to the twists 76 of the first channel 70A.
  • FIG. 5 schematically illustrates cooling of a component 60 using the cooling system 65.
  • a cooling fluid 69 is introduced into both the first channel 70A and the second channel 70B.
  • additional channels, positioned in pairs, could be incorporated into the cooling system 65. Due to the twist of the first and second channels 70A, 70B, the cooling fluid 69 is forced to flow along the first swirl flow path S1 and the second swirl flow path S2 inside of the first and second channels 70A, 70B.
  • the cooling fluid 69 naturally induces vortices VI, V2 as it is discharged along a surface 100 of the component 60 through the first and second outlets 80, 82 as film injection at the surface 100.
  • the flow of the cooling fluid 69 along the first and second swirl flow paths S1, S2 generates a pair of counter vortices V3, V4 that counteract the vortices VI, V2, thereby improving heat transfer with only modest pressure loss and reducing aerodynamic loss in the cooling fluid 69.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Bauteil (60), Folgendes umfassend:
    eine Wand (72);
    einen ersten Kanal (70A), der sich zumindest teilweise durch die Wand (72) zu einem ersten Durchlass erstreckt;
    einen zweiten Kanal (70B), der sich neben dem ersten Kanal (70A) und zu einem zweiten Durchlass erstreckt; und
    wobei der erste Kanal (70A) konfiguriert ist, eine Kühlflüssigkeit entlang eines ersten Drallströmungspfads zu leiten und der zweite Kanal (70B) konfiguriert ist, die Kühlflüssigkeit entlang eines zweiten Drallströmungspfads zu leiten, der dem ersten Drallströmungspfad gegenüberliegt;
    gekennzeichnet dadurch, dass ein Querschnitt durch den ersten Kanal und den zweiten Kanal (70A, 70B) elliptisch ist.
  2. Bauteil (60) nach Anspruch 1, wobei das Bauteil (60) aus einer Klinge, einer Schaufel, einer äußeren Klingenluftabdichtung (BOAS), einem Brennkammermantel und einem Turbinenaustrittsgehäusemantel besteht.
  3. Bauteil (60) nach Ansprüchen 1 oder 2, wobei wenigsten einer des ersten und zweiten Kanals (70A, 70B) ein Mikrokanal ist.
  4. Bauteil nach einem der vorhergehenden Ansprüche, wobei jeder des ersten und zweiten Kanals (70A, 70B) einen Maximaldurchmesser von weniger als 0,635 Millimetern einschließt.
  5. Bauteil (60) nach einem der vorhergehenden Ansprüche, wobei sich jeder des ersten und zweiten Kanals (70A, 70B) entlang einer Achse erstreckt und eine Vielzahl an Windungen einschließt.
  6. Bauteil nach einem der vorhergehende Ansprüche, wobei wenigstens einer des ersten und zweiten Kanals (70A, 70B) sich in wenigstens einer vollen Drehung um eine Achse windet, die sich durch wenigstens einen des ersten und zweiten Kanals erstreckt.
  7. Bauteil nach einem der vorhergehenden Ansprüche, wobei wenigstens einer des ersten und zweiten Kanals(70A, 70B) spiralförmig geformt ist.
  8. Bauteil nach einem der vorhergehenden Ansprüche, der erste und zweite Kanal (70A, 70B) räumlich getrennt und parallel zueinander angeordnet sind.
  9. Gasturbinentriebwerk (20), Folgendes umfassend:
    ein Bauteil (60) nach einem der vorhergehenden Ansprüche, das sich in einen Kernflusspfad des Gasturbinentriebwerks erstreckt.
  10. Gasturbinentriebwerk (20) nach Anspruch 9, wobei zumindest einer des ersten und zweiten Kanals (70A, 70B) ein Mikrokanal ist, der einen Maximaldurchmesser von weniger als 0,635 Millimetern hat.
  11. Gasturbinentriebwerk (20) nach Anspruch 9 oder 10, wobei jeder des ersten und zweiten Kanals (70A, 70B) spiralförmig geformt ist, und wobei sich vorzugsweise jeder des ersten und zweiten Kanals (70A, 70B) entlang einer Achse erstreckt und eine Vielzahl an Windungen einschließt.
  12. Gasturbinentriebwerk (20) nach Ansprüchen 9-11, wobei sich wenigstens einer des ersten und zweiten Kanals (70A, 70B) in mehrfachen vollen Drehungen um eine Achse windet, die sich durch wenigstens einen des ersten und zweiten Kanals erstreckt und wobei der erste und zweite Kanal (70A, 70B) vorzugsweise räumlich voneinander getrennt und parallel zueinander angeordnet sind.
  13. Verfahren zum Kühlen eines Bauteils (60) eines Gasturbinentriebwerks (20) nach einem der Ansprüche 1-8, Folgendes umfassend:
    Schaffen eines Paars von Gegenwirbeln entlang einer Oberfläche des Bauteils, um einem Paar von naturgemäß ausgelösten Wirbeln entgegenzuwirken, die in Verbindung mit Filmeinspritzung an der Oberfläche stehen.
  14. Verfahren nach Anspruch 13, wobei der Schritt des Schaffens das Leiten einer Kühlflüssigkeit entlang eines ersten Drallströmungspfads des ersten Kanals (70A) des Bauteils und eines zweiten, entgegengesetzten Drallströmungspfads des zweiten Kanals (70B) des Bauteils einschließt.
  15. Verfahren nach Anspruch 14, folgenden Schritt umfassend:
    Ableiten der Kühlflüssigkeit durch einen ersten Auslass des ersten Kanals (70A) und durch einen zweiten Auslass des zweiten Kanals (70B) an der Oberfläche, um die Filmeinspritzung bereitzustellen.
EP14767715.7A 2013-03-15 2014-03-13 Bauteil, zugehöriges gasturbinentriebwerk und verfahren zum kühlen eines bauteils Active EP2971671B1 (de)

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US201361788682P 2013-03-15 2013-03-15
PCT/US2014/025268 WO2014151239A1 (en) 2013-03-15 2014-03-13 Gas turbine engine component cooling channels

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WO2014151239A1 (en) 2014-09-25
US10378362B2 (en) 2019-08-13
US20160010467A1 (en) 2016-01-14
EP2971671A1 (de) 2016-01-20
EP2971671A4 (de) 2016-11-02

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